Ongoing research is presented directed toward the development of a Mach-scaled rotor model with piezoelectric bender-actuated trailing-edge flaps for individual blade control of helicopter vibration. First, an analytical model is developed for the coupled actuator-flap-rotor dynamic response in hover. Then, the analysis is validated by using test data obtained by hover testing a 6-ft (1.82-m)-diam, Froude-scaled rotor with piezo-bender-actuated trailing-edge flaps. The analytic model shows good correlation with experimental lap deflections and oscillatory hub loads. For the Froude-scaled model flap deflections of +/-4 to +/-8 deg, for 1 to 5 /rev flap excitation, were achieved at 900 rpm. This flap activation resulted in a 10% variation in the steady rotor thrust level at 6 deg collective. Next, two Mach-scaled rotor blades with piezo-bender actuation were designed and fabricated. The rotor was tested in the vacuum chamber, and flap deflections of +/-8 deg were achieved in vacuum at the Mach-scaled operating speed of 2000 rpm. The analysis predicts that in hover flap deflections of +/-5 deg can be achieved at 2000 rpm. Future work will involve hover tests followed by forward flight tests in the wind tunnel to confirm these predictions and demonstrate concept feasibility.
Analysis and testing of mach-scaled rotor with trailing-edge flaps
Modellierung und Test eines bezüglich der Mach-Zahl maßstabsgetreuen Drehflügels mit einem Piezoaktuator zur Schwingungsdämpfung
AIAA Journal ; 38 , 7 ; 1113-1124
2000
12 Seiten, 28 Bilder, 1 Tabelle, 24 Quellen
Aufsatz (Zeitschrift)
Englisch
Wind Tunnel Testing of a Mach-Scaled Rotor Model with Trailing-Edge Flaps
British Library Conference Proceedings | 2000
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